EP0888201A1 - Assemblage determinant d'aileron - Google Patents

Assemblage determinant d'aileron

Info

Publication number
EP0888201A1
EP0888201A1 EP97917554A EP97917554A EP0888201A1 EP 0888201 A1 EP0888201 A1 EP 0888201A1 EP 97917554 A EP97917554 A EP 97917554A EP 97917554 A EP97917554 A EP 97917554A EP 0888201 A1 EP0888201 A1 EP 0888201A1
Authority
EP
European Patent Office
Prior art keywords
web
chords
spar
coordination
wing
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP97917554A
Other languages
German (de)
English (en)
Other versions
EP0888201B1 (fr
EP0888201A4 (fr
Inventor
Clayton L. Munk
Paul E. Nelson
David E. Strand
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Boeing Co
Original Assignee
Boeing Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=21762879&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP0888201(A1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Boeing Co filed Critical Boeing Co
Publication of EP0888201A1 publication Critical patent/EP0888201A1/fr
Publication of EP0888201A4 publication Critical patent/EP0888201A4/fr
Application granted granted Critical
Publication of EP0888201B1 publication Critical patent/EP0888201B1/fr
Anticipated expiration legal-status Critical
Revoked legal-status Critical Current

Links

Classifications

    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B19/00—Programme-control systems
    • G05B19/43—Programme-control systems fluidic
    • G05B19/44—Programme-control systems fluidic pneumatic
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P21/00—Machines for assembling a multiplicity of different parts to compose units, with or without preceding or subsequent working of such parts, e.g. with programme control
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
    • B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
    • B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
    • B25B11/005—Vacuum work holders
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
    • B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
    • B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
    • B25B11/005—Vacuum work holders
    • B25B11/007—Vacuum work holders portable, e.g. handheld
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
    • B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
    • B25B5/00—Clamps
    • B25B5/06—Arrangements for positively actuating jaws
    • B25B5/12—Arrangements for positively actuating jaws using toggle links
    • B25B5/122—Arrangements for positively actuating jaws using toggle links with fluid drive
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
    • B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
    • B25B5/00—Clamps
    • B25B5/16—Details, e.g. jaws, jaw attachments
    • B25B5/163—Jaws or jaw attachments
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B19/00—Programme-control systems
    • G05B19/02—Programme-control systems electric
    • G05B19/18—Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form
    • G05B19/401—Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by control arrangements for measuring, e.g. calibration and initialisation, measuring workpiece for machining purposes
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B19/00—Programme-control systems
    • G05B19/02—Programme-control systems electric
    • G05B19/18—Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form
    • G05B19/408—Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by data handling or data format, e.g. reading, buffering or conversion of data
    • G05B19/4083—Adapting programme, configuration
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
    • B23P2700/01—Aircraft parts
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B2219/00—Program-control systems
    • G05B2219/30—Nc systems
    • G05B2219/36—Nc in input of data, input key till input tape
    • G05B2219/36503—Adapt program to real coordinates, software orientation
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B2219/00—Program-control systems
    • G05B2219/30—Nc systems
    • G05B2219/49—Nc machine tool, till multiple
    • G05B2219/49136—Vacuum pads hold workpiece during machining
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P90/00—Enabling technologies with a potential contribution to greenhouse gas [GHG] emissions mitigation
    • Y02P90/02—Total factory control, e.g. smart factories, flexible manufacturing systems [FMS] or integrated manufacturing systems [IMS]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49764—Method of mechanical manufacture with testing or indicating
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining
    • Y10T29/49885—Assembling or joining with coating before or during assembling
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining
    • Y10T29/49895—Associating parts by use of aligning means [e.g., use of a drift pin or a "fixture"]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining
    • Y10T29/49904—Assembling a subassembly, then assembling with a second subassembly

Definitions

  • This invention relates to a method and apparatus for assembling wing spars and ribs to close tolerances, and more particularly, to a method and apparatus for assembling wing spars and ribs with extreme and unprecedented precision to produce wing components having extremely close conformance to the original engineering design, with significantly reduce tooling expense.
  • the tooling is intended to accurately reflect the original engineering design of the product, but using the conventional tooling concept in which the tooling sets the configuration of the final assembly, there are many steps between the original design of the product and the final manufacture of the tool. It is not unusual that the tool as finally manufactured produces missized spars or wing components that would be outside of the dimensional tolerances of the original spar or spar component design without extensive, time consuming and costly hand work to correct the tooling-induced errors. More seriously, a tool that was originally built within tolerance can become out of tolerance from the hard use it typically receives in the factory.
  • dimensional variations caused by temperature changes m the factory can produce a variation in the final part dimensions as produced on the tool, particularly when a large difference in the coefficient of thermal expansion exists between the tooling and the spar, as in the usual case where the tooling is made of steel and the spar components are made of aluminum. Since dimensions in airplane construction are often controlled to within 0.005", temperature induced dimensional variations can be significant.
  • Hand drilling of the part on the tool can produce holes that are not perfectly round or normal to the part surface when the drill is presented to the part at an angle that is slightly nonperpendicular to the part, and also when the drill is plunged into the part with a motion that is not perfectly linear.
  • Parts can shift out of their intended position when they are fastened in non-round holes, and the nonuniform hole- to-fastener interference m a non-round hole lacks the strength and fatigue durability of round holes.
  • the tolerance buildup on the spar subassemblies can result m significant growth from the original design dimensions, particularly when the part is located on the tool at one end of the part, forcing all of the part variation m one direction instead of centering it over the true intended position.
  • Spar components are typically fastened together with high interference fasteners and/or fasteners in cold worked holes.
  • Interference fasteners such as rivets and lock bolts, and cold working of a fastener hole, both create a pattern of stress m the metal around the hole that improves the fatigue life of the assembled ]omt, but a long line of such stress patterns causes dimensional growth of the assembly, primarily m the longitudinal direction, and also can cause an elongated part to warp , or "banana" along its length.
  • Wing major spar tooling is expensive to build and maintain within tolerance, and requires a long lead time to design and build.
  • the enormous cost and long lead time to build wing spar tooling is a profound deterrent to redesigning the wing of an exist model airplane, even when new developments in aerodynamics are made, because the new design would necessitate rebuilding the wing spar tools.
  • One existing system for automatic drilling, fastener installation and tightening is shown in U.S. Patent No. 5,xxx,xxx by Banks et al. entitled "Automated Spar Assembly Tool". It produces spars accurately, but is a costly system to build and maintain.
  • an object of this invention to provide a method of manufacturing long, large and heavy assemblies such as airplane wing spars and ribs from flexible and semi-flexible parts and subassemblies in accordance with an original engineering design instead of the tooling.
  • Another object of the invention is to provide a method of manufacturing airplane wing spars and ribs using intrinsic features of the component parts to allow them to self locate and determine assembly dimensions and contours rather than using conventional tooling to determine the placement of the parts relative to one another and the contour of the assembly.
  • It is yet another object of this invention to provide a system for manufacturing airplane wing spars that is inherently more accurate than the prior art and produces structures in which the parts are consistently located more accurately on the structure with closer conformance to the tolerance specified by the engineering design.
  • It is yet a further object of the invention to provide a system for manufacturing airplane wing spars that is faster, more flexible, and less expensive than the prior art traditional techniques and requires less factory space and is less dependent upon the skill of workers to produce parts within the engineering tolerances specified.
  • Still a further object of this invention is to provide a method and apparatus which facilitates the manufacturing of airplane wing spars with a precision and consistency that enables airplane wings to be built within tolerance specified in the original engineering design.
  • Another still further object of the invention is to provide a method for building airplane wing spars having a sequence of operations arranged to apply critical features to the detail parts or subassemblies after the spar or spar component has been distorted by operations, such as installation of interference fasteners, that distort the spar or spar component.
  • Figs. 1-6 are sequential schematic diagrams showing the major assembly steps performed on the spar web and other components while they are supported on a line of stanchions, shown in Fig. 8, during assembly of an airplane wing spar in accordance with this invention;
  • Fig. 7A is a perspective view of a spar built in accordance with the process and on the apparatus of this invention
  • Fig. 7B is an enlarged perspective view of the inboard end of the spar shown in Fig. 7A;
  • Fig. 8 is a perspective schematic view of a wing spar assembly cell in accordance with this invention.
  • Fig. 9 is a plan view of the Fig. 10 is a plan view of one side of the wing spar assembly cell shown in Fig. 8, in the region of the bend;
  • Fig. 11 is a perspective view the portion of the spar assembly cell assembly cell shown in Fig. 10;
  • Fig. 12 is a perspective view of one of the stanchions shown in Fig. 11;
  • Fig. 13 is a perspective view of one of the stanchions having a spar web support arm shown in Fig. 11;
  • Figs. 14 is a perspective view of a slightly modified spar support stanchion showing the clamps of temporary chord locators
  • Fig. 15 is a view like Fig. 14, but showing the spar web removed for purposes of illustration;
  • Fig. 16 is an enlarged view of a portion of Fig. 15;
  • Fig. 17 is a perspective view of the back right side of the structure shown in Fig. 14;
  • Fig. 18 is an enlarged perspective view of a portion of Fig. 17;
  • Fig 19 is an enlarged perspective view of the back left side of the structure shown in Fig. 18;
  • Fig. 20 is a perspective view of chord locator tools holding chords in place on the top and bottom edges of the inboard portion the spar web;
  • Fig. 21 is a side elevation of a slightly modified form of the chord locator tools shown in Fig. 20;
  • Fig. 22 is an enlarged side elevation of the top end of a chord locator tool like the one shown in Fig. 21, but having chord referencing surfaces set at a different angle, corresponding to the angle of the chord at a different position along its length;
  • Fig. 23 is a side elevation of the top end of a chord locator tool having a chord locator reference surface on a pivoted heel piece;
  • Fig. 24 is a side elevation of the structure shown in Fig. 22, with the clamp in its open position;
  • Fig. 25 is an enlarged side elevation of the bottom end of a chord locator tool
  • Fig. 26 is an enlarged perspective view of the bottom end of the chord locator tool shown in Fig. 25;
  • Fig. 27 is a side elevation of a tool for locating the position of the spar chords in the "X" direction;
  • Fig. 28 is a perspective view of the top end of the Chord- X tool shown in Fig. 27;
  • Fig. 29 is a perspective view of a clamping, drilling and fastener feed end effector shown in Fig. 8 to be carried by the post mill and perform fastening operations;
  • Fig. 30 is a schematic view of a computer architecture and process for converting data from a digital product definition to instruction in a machine tool controller for perform certain assembly operations;
  • Fig. 31 is a perspective view from the top of the pivoting base plate shown in Figs. 8-11;
  • Fig. 32 is a perspective view from the bottom of the pivoting base plate shown in Fig. 31;
  • Fig. 33 is a perspective view of the support arm shown in Figs. 10, 11 and 13;
  • Fig. 34 is a perspective view of a positioning assembly at the distal end of the support arm shown in Fig. 33; and Figs. 35 and 36 are perspective views of the positioning assembly shown in Fig. 34 in different stages of assembly.
  • a representative airplane wing spar will be described.
  • an airplane wing includes two spars 30 extending lengthwise, or “spanwise", of the wing and spaced apart in a "chordwise” direction.
  • Wing ribs extend chordwise between the spars 30 and are fastened to vertical rib posts 35, shown in Figs. 7A and 7B, which are adhered and sealed to the spars 30 and fastened thereto by numerous fasteners.
  • Top and bottom chords 40 and 42 are adhered and sealed to top and bottom edges of a spar web 45, and fastened thereto with numerous fasteners such as rivets, bolts, lock bolts, Hi-Locks, and the like, which are widely used in the aerospace industry, and are well understood and reliable.
  • top and bottom chords 40 and 42 each have a vertical flange that is secured to the spar web 45, and an angled top or bottom flange to which a top or bottom wing panel is attached.
  • the vertical position of the chords 40 and 42 on the web 45 is critical because it determines the spacing at the spars 30 between the top and bottom wing panels.
  • the position of the rib posts 35 on the spar is critical because they determine the position of the ribs which in turn determine the contour of the wing panel.
  • a bend or "kink” 46 at a "K" axis, shown in Figs. 7A and 7B, is found on most wing spars so that the spars can conform to the designed position of the front and rear outside edges of the wing box.
  • the space defined between the front and rear wing spars and the top and bottom wing panels, that is, the outside structural elements of the wing box, is normally used as the airplane fuel tank, so the inside surfaces of the wing spars are commonly refered to as the "wet” sides and the outside surfaces are refered to as the “dry” sides. That convention will be used herein.
  • the rib posts 35 are attached to the wet side of the spar and a multiplicity of vertical stiffeners 47 are adhered and sealed to the dry side of the spar web 45 and fastened thereto by a multiplicity of fasteners.
  • a spar assembly process m accordance with this invention for assembling an airplane wing spar 30 begins with configuring a reconfigurable assembly cell 50, shown m Figs. 8 and 9, for the particular size and design of the wing spar to be assembled in the cell 50.
  • the assembly cell has a line of stanchions 52 mounted on rails 54, as shown m Figs. 10 and 11, so the stanchions can be moved in the "X" direction parallel to the plane of the spar 30 to position them at the desired position lengthwise of the spar.
  • Two or more lateral positioning devices, such as the "pogo" devices 56 illustrated in Figs. 12 and 13, are mounted on each of the stanchions 52 for establishing the lateral position of a spar web 45 m the "Z" direction m the cell 50.
  • a support arm 60 is attached to selected ones of the stanchions 52 along the row of stanchions, as shown m Figs. 10 and 11, to carry the weight of the spar web 45.
  • a primary index pm 64 m the end of one of the support arms 60 is received in a coordination hole predrilled in the spar web 45 to position the web accurately on the stanchions m the "X" and "Y" directions, m an orientation that is longitudinally horizontal and laterally upright, as shown in Fig. 14.
  • Secondary index pins 66 on the other support arms 60 are engaged in coordination holes, also predrilled in the web 45, to support the web vertically.
  • the secondary index pins 66 are horizontally compliant, as described m detail below, to accommodate longitudinal growth m the spar web 45 caused by fastener installation.
  • Vacuum in vacuum cups 70 on the ends of the pogos 56 draw the web 45 against front facing surfaces 72 within the vacuum cups 70 to hold the web m the lateral "Z" position established by the extension of the pogos 56.
  • a machine tool such as a CNC post mill 75 shown in Figs. 8 and 9, is supported for longitudinal movement on rails 77 in the cell 50.
  • the post mill 75 has an elongated arm 80 that can be driven in a self-parallel fashion on the body of the post mill 75 in the vertical or "Y" direction, and can also be extended lengthwise.
  • the body of the post mill 75 can be provided with the capability to rotate about its vertical axis if, as described herein, the cell has a line of stanchions on both sides of the cell so the post mill can be performing operations on one side while workers are installing parts, removing completed spars or doing other manual operations on the other side.
  • the arm 75 has a wrist that can rotate about the axis of the arm 75 and can tilt sideways.
  • a gripping device at the distal end of the wrist has mechanical and power connections for holding and powering one or more end effectors 85 for performing the various functions needed in the assembly cell 50. These axes of motion permit the post mill 75 to position the end effector in any desired position and orientation within the reach of the arm 80.
  • the post mill 75 shown is supplied by Ingersol Milling Machine Company, but other machine tools, such as a Henri Line 1 gantry mounted 5-ax ⁇ s tool, or an "Aeroflex" six-axis positioner made by Pegard Products, Inc. in Machesney Park, 111. could be used.
  • the required capabilities are precision and repeatability m spindle positioning, which in this application is about ⁇ 0.005", and operation under control of a machine controller that can be programmed to incorporate digital product definition data originating from an engineering authority for the wing and wing components, so that coordination features specified by the digital product definition can be placed accurately and repeatably by the machine tool 75.
  • coordination features such as coordination holes and machined coordination surfaces
  • These coordination features are used to position parts and components relative to each other where they are pinned and fastened, thereby eliminating or drastically reducing the need for fixed hard tooling that previously was used to located the parts and components relative to each other.
  • the coordination features thus determine the relative position of the parts and components that comprise the assembly, and thereby determine the size and shape of the assembly, independently of most tooling.
  • the upper and lower spar chords 40 and 42 are loaded, as illustrated in Fig. 1, onto temporary chord locators 90 hanging on the pogos 56 for holding the spar chords adjacent to the spar web position in preparation for transfer to the spar web 45.
  • the spar 30 is built in the inverted position because the lower edge of the spar diverges where the spar becomes wider at the inboard end, so building the spar in the inverted position reduces the reach of the scaffolding that may be needed by workers to reach the upper parts of the spar. Therefore, the drawings show the "upper" chord 40 in the bottom position and the "lower" chord 42 m the top position.
  • chords 40 and 42 are held in position on the temporary chord locators 90 with over-center clamps 92 on the top and bottom ends of the chord locators 90. Sealant is applied to the vertical flange faying surface of the spar chords 40 and 42 where they will contact the spar web 45.
  • the spar web 45 is loaded onto the index pins 64 and 66 on the arms 60 and is drawn against the facing surfaces 72 of the pogos 56 by vacuum in the vacuum cups 70.
  • chord-Y tools 95 each of which is positioned on the spar web 45 by way of a pair of indexing pins 100 and 102 in chord tool coordination holes drilled with extreme positional accuracy in the spar web 45 with a drill controlled by the CNC post mill 75.
  • clamps 105 and 107 are attached to the top and bottom ends of each chord tool 95.
  • the clamps on the chord-X tools 95 shown in Fig. 20 are slightly different from those shown in Figs. 21-25 to show that different types of clamps can be used.
  • the upper clamp 105 has reference surfaces 110 and 112, shown in Fig.
  • the lower clamp 107 has reference surfaces 114 and 116 for precisely locating the upper chord 40 at the correct vertical position on the web 45.
  • the reference surfaces 112 and 114 may be on heel blocks 113 and 115 that are pivotally connected to the chord-Y tools to conform to the angle of the top and bottom flanges of the spar chords, as shown in Figs. 23 and 25.
  • the chords 40 and 42 are transferred from the temporary chord locators 90 onto the chord-Y tools 95 and into position against the chord tool reference surfaces and against the spar web 45 by opening the chord tool clamps, as shown in Fig. 23, and sliding the temporary chord locators 90 on the pogos 56 until the chords contact the web 45.
  • chord-X tool 121 was previously attached to the web 45 by index pins 122 and 124 extending into coordination holes accurately drilled into the web by the post mill 75 at the same time that the coordination holes for the chord-Y tools 95 are drilled.
  • chords 40 and 42 now indexed accurately in the "X" direction with the chord-X tool 121, are pushed into position against the reference surfaces 110-116 of the chord-Y tool 95 to position the chords 40 and 42 against the top and bottom edges of the web 45 accurately in the "Y" direction.
  • the chords 40 and 42 are secured in place against the reference surfaces 110-116 by the chord-Y tool clamps 105 and 107.
  • a probing routine is now performed to accommodate the deflection of the stanchions 52 and support arms 60 under the weight of the spar web 45 and chords 40 and 42.
  • a probe held by the post mill arm 80 probes the primary index pin 64 and one or more secondary index pins 66 to locate their actual position.
  • a suitable probe for this purpose would be a Renishaw contact tactile probe Model No. MP ⁇ made by the Renishaw Company in Onendagua, New York, although other probes available from other sources could also be used.
  • the machine controller for the post mill 75 uses the actual positions of the index pins as located by the probe to normalize the part program in the controller to make it conform to the actual position of the parts on the stanchions 52.
  • chords are now fastened to the web 45 with the end effector 85, shown conceptually in Figs. 1, 3-7 and 29.
  • the end effector 85 is carried and positioned at the locations along the web 45 by the post mill arm 80, as shown in Fig. 8.
  • a clamp 130 on the end effector 85 has a C-frame 132 with an anvil 134 on its distal end that engages the vertical flange of the chords 40 and 42 on the "wet" side of the spar.
  • a pressure foot 136 is aligned opposite the anvil on the other side of the C-frame 132 where it engages the spar web on the opposite side of the web from the anvil and is actuated with a pneumatic cylinder to exert a clamp- up force on the order of 1000-1500 pounds to clamp the chords to the web during drilling and fastener insertion.
  • a frequency controlled spindle motor mounted within the end effector 85 behind the pressure foot 136 rotates and feeds a drill bit to drill holes through an opening in the pressure foot 136 while chips are vacuumed away through a vacuum hose 142.
  • the drill spindle retracts and a hole probe 144 mounted behind the anvil 134 probes the hole drilled through the web and chord flange through an opening in the anvil 134.
  • a shuttle moves behind the pressure foot to align a fastener feed holder with the newly drilled hole, and an interference fit fastener is fed through a line 148 to the holder.
  • a pneumatic hammer drives the fastener into the hole.
  • the pressure foot now unclamps and moves to the next fastener location. Securing the fasteners with swage collars or nuts is performed by workers on the outside of the cell 50 where there is no danger of injury from the post mill 75 inside the cell 50. The workers also remove the chord-Y tools 95 as the post mill 75 approaches their position on the spar 30.
  • the post mill uses the same end effector 85 or a separate drill-only end effector to drill coordination holes for stiffeners and rib posts.
  • a master digital model 150 of the spar in the engineering authority for the airplane manufacturer specifies the location of the coordination holes for the rib posts and the stiffeners, and the part program which controls the movement of the post mill 75 is derived from that master digital model 150.
  • the stiffeners 47 and rib posts 35 have coordination holes predrilled when they are manufactured, or the coordination holes are drilled in a separate dedicated fixture.
  • the coordination holes correspond to the locations of the coordination holes drilled in the web 45 by the end effector 85.
  • the coordination holes in the rib post 35 or stiffener 47 are aligned with the corresponding coordination holes drilled in the web 45, the part is positioned with extreme accuracy on the web 45 in accordance with the engineering design as represented by the digital model.
  • the flange of the rip post or stiffener has sealant applied to its faying surface with the web 45 and is temporarily fastened to the web with clecos or some other removable temporary fastener.
  • the end effector 85 is positioned by the post mill arm 80 to clamp the part flange to the web, drill a fastener hole and insert a fastener as described above for the chords 40 and 42.
  • the clamp-up force is sufficient to squeeze out excessive sealant so the drill chips do not have sealant on them which could foul the chip vacuum system, and prevents interlaminar burrs from intruding between the part 35 or 47 and the web 45.
  • the semi-automated process mentioned above uses the same coordination hole drilling process for establishing the location of the rib posts 35 and stiffeners 47 described above.
  • the holes must be drilled without clamp-up, so interlaminer burrs are likely to occur. Therefore, the parts are temporarily fastened to the web 45 with clecos or the like and the fastener holes are drilled with the end effector 85 or another drilling-only end effector. The clecos are then removed and the parts and web are deburred. Sealant is applied to the faying surfaces and the parts are again temporarily fastened to the web 45 with clecos or the like.
  • Interference fasteners are inserted with pneumatic drivers and the fasteners are secured with swage collars or nuts in the same manner as described above.
  • the position of certain critical features may now be probed and the part program updated with the actual dimensions of the assembled spar.
  • coordination holes are drilled with extreme precision, entirely unaffected by the growth during assembly, for two fittings for connection of a main landing gear beam and certain other fittings such as flap support fittings and aileron hinge line brackets.
  • the spar is now complete and is removed from the cell by crane and transferred to the wing line for installation in a wing.
  • the digital product definition or digital model 150 is the ultimate engineering authority for the product, in this case, a particular model airplane. It exists on a master computer 152 in a computer-aided design program as the digital model 150 which includes all the dimensions, tolerances, materials and processes that completely define the product.
  • the dimensional data from the model 150 is provided in a file to an NC programmer or an automatic translator where it is used to create a dataset 154 and machine instructions, such as cutter type and size, feed speeds, and other information used by a controller of the post mill 75 to control the operation of the arm 80.
  • the dataset and machine instructions are launched in a post processor 156 where they are converted to a machine readable file 158 that is transmitted to a data management system 160 where it is stored for use by the controllers 162 of the post mill 75.
  • the file 72 is transmitted over phone lines 164 or other known means of communication to the machine tool controller 162 for use by the controller in operating the post mill 75.
  • the bend or kink 46 in the spar is at an angle that is unique to each model airplane.
  • the stanchions 52 on the inboard side of the bend 46 are mounted on a plate 170 that is pivotally mounted for rotation about a vertical axis 172 that is set to coincide with the "K" axis of the bend 46.
  • the upper surface of the plate 170 has a pair of parallel grooves 174 to receive the tracks 54 on which about six stanchions 52 are slidably mounted.
  • a spherical socket 176 on the end of a wing 178 projecting from the front inner corner of the plate 170 has a receives a spherical bearing ball which enable the plate to swivel about the axis 172 when lifted by air bearings on the underside of the plate 170.
  • a tab 180 projecting from the rear distal end of the plate 170 has a precision index hole 182 for receiving an index pin by which the plate can be indexed to a precision hole in a plate fixed in the floor.
  • Configuring the cell 50 for assembling a spar of a particular model airplane is a simple matter of mobilizing the plate 170 with its air bearings and moving it to the position specified at which the index hole 182 in the tab 180 aligns with the index hole in the floor plate, and turning off the air bearing to allow the plate 170 to settle into hard contact with the floor.
  • the plate 170 is an aluminum casting about 27 feet long and 6 feet wide. It weighs on the order of 5000 pounds, even with an X-brace construction on its underside, shown in Fig. 32, so its weight and the attachments at the tab 182 and the wing 178 anchor it securely to the floor.
  • a series of index holes 185 one for each model airplane spar to be built on that cell 50, is drilled for each stanchion, as shown in Figs. 12-15.
  • the position of the stanchions 52 along the rails is then easily set by inserting an index pin 187 in a tab 190 of the front of each stanchion 52 in the proper index hole 185, which are suitably labeled to facilitate quick and sure identification by the workers for that purpose.
  • the vertical position of the pogos 56 are set by adjusting servomotors 192 which drive ball screws threaded into a slide mounted on vertical guides in the stanchions 52.
  • the post mill 75 probes the pogos to confirm that the correct vertical position has been attained and issues a correction to the servomotors if the vertical position is incorrect.
  • the pogos 56 are all fully extended by pressurizing air cylinders 194 in which the pogo rods 196 are mounted.
  • the cylinders are vented and the post mill 75 extends its arm 80 into contact with the facing surface 72 of the pogo to push each one back to the desired position, whereupon a pneumatic lock 200 is actuated to lock the pogos 56 in the desired position.
  • the support arms 60 are indexed to the stanchions 52 by index pins 202 and secured by fasteners 204.
  • an end plate 206 on the end of each support arm 60 carries a positioning assembly 210 for the index pins 64 and 66.
  • the first step in setting the position of the index pins 64 and 66 is to "face off" or mill the face of the end plates 206 so they lie on a vertical plane and at the correct lateral position in the cell 50.
  • a vertical dovetail groove plate 212 is positioned on the end plate 206 by index pins in coordination holes predrilled in the vertical dovetail rabbet plate 212 and aligned with corresponding coordination holes drilled in the end plate 206 by the post mill 75. As best shown in Fig.
  • a dovetail tenon plate 215 having a vertical dovetail tenon on its back surface and a horizontal dovetail tenon on its front surface is mounted for vertical adjustment on the vertical dovetail rabbet plate 212, with the vertical tenon on the plate 215 in the rabbet of the plate 212, and is locked in place by a top plate 216 when it is at the correct height in the "Y" direction, as verified by the probe on the post mill arm 80.
  • a horizontal dovetail rabbet plate 218 is mounted on the horizontal tenon of the dovetail tenon plate 215 for horizontal adjustment parallel to the "X" axis.
  • a pin 220 attached to and protruding forwardly from the dovetail tenon plate 215 is received in a lock block 222 to which a mounting plate 224 for the index pins 64 and 66 are attached.
  • the lock block 222 has a vertical hole opening in its lower edge for receiving a ball lock pin 226 which passes up through a corresponding vertical hole in a base plate 230, in turn attached to the lower edge of the dovetail tenon plate 215.
  • the lock block 222 can be locked in position against horizontal movement while it s position is being probed for position by the tactile probe held by the post mill arm 80 during the probing routine, and then can be freed for horizontal movement in the "X" direction during longitudinal growth of the spar 30 by virtue of thermal expansion and installation of interference fasteners.
  • the ball lock pin 226 on the positioning assembly 210 on which the primary index pin 64 is mounted will be retained in its locked position to establish the reference "X" position from which "X" axis growth occurs.
  • a system is thus disclosed which is usable for assembling airplane wing ribs and spars to a high degree of precision.
  • the determinant assembly concept embodied in this disclosure utilizes the spatial relationships between key features of detail parts and subassemblies, as defined in the digital design and represented by coordination holes and other coordination features put into the parts and subassemblies by a numerically controlled tool, using original part design data from the engineering authority, to control the relative location of detail parts in subassemblies and the relative relationship of subassemblies to each other, making the parts and subassemblies self locating.
  • This concept eliminates the need for traditional hard tooling used for decades in the air frame industry and for the first time enables assembly of large, heavy, flexible and semi-flexible mechanical structures wherein the contour of the structure and the relative dimensions within the structure are determined by the parts themselves rather than the tooling.
  • the wing spar can now be built to accommodate distortion created by manufacturing processes, such as interference fasteners and cold working, so that attachment of critical features on the wing at precisely accurate positions specified by the engineering design can be scheduled in the manufacturing process after distortion by the upstream processes which would have affected their position or orientation on the wing.
  • the factory can now manufacture wing spars of any shape and size for which engineering data is provided, within the physical range of the CNC machine tools, and do so faster and with far greater precision than was possible with fixed tooling.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Automation & Control Theory (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Human Computer Interaction (AREA)
  • Transportation (AREA)
  • Automatic Assembly (AREA)
  • Jigs For Machine Tools (AREA)
  • General Factory Administration (AREA)
  • Gripping Jigs, Holding Jigs, And Positioning Jigs (AREA)
  • Machine Tool Sensing Apparatuses (AREA)
  • Drilling And Boring (AREA)

Abstract

Cette invention concerne un procédé et un appareil de fabrication de longerons d'ailes (30). Ledit appareil comporte un dispositif (52) qui maintient les âmes des longerons (45) pendant le perçage et le détourage effectués par des machines-outils (85) précises à commande numérique. Il comporte également un instrument à cordes (95) conçu pour positionner une paire de cordes (40, 42) sur une âme de longeron (45). Le procédé de l'invention consiste à positionner une âme de longeron sur ledit dispositif (52), à déterminer la position réelle de l'âme de longeron (45) sur le dispositif (52) par rapport à un emplacement connu fixe, à normaliser une machine-outil (85) en fonction de la détermination effectuée, à percer dans l'âme de longeron (45) des trous de coordination de l'instrument positionneur de cordes, à monter temporairement l'instrument à cordes (95) sur l'âme de longeron (45) en faisant passer des attaches à travers lesdits trous de coordination et en faisant correspondre les trous de l'âme de longeron (45) supportant les cordes supérieure et inférieure (40, 42) sur l'instrument à cordes (95), à serrer les cordes (40, 42) contre l'âme de longeron (45), puis à fixer les cordes (40, 42) à l'âme de longeron (45) en faisant passer des attaches à travers les trous correspondants de l'âme de longeron.
EP97917554A 1996-03-22 1997-03-21 Assemblage determinant d'aileron Revoked EP0888201B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US1398696P 1996-03-22 1996-03-22
US13986P 1996-03-22
PCT/US1997/004453 WO1997034733A1 (fr) 1996-03-22 1997-03-21 Assemblage determinant d'aileron

Publications (3)

Publication Number Publication Date
EP0888201A1 true EP0888201A1 (fr) 1999-01-07
EP0888201A4 EP0888201A4 (fr) 2002-05-15
EP0888201B1 EP0888201B1 (fr) 2006-05-31

Family

ID=21762879

Family Applications (2)

Application Number Title Priority Date Filing Date
EP97917567A Expired - Lifetime EP0888202B1 (fr) 1996-03-22 1997-03-21 Montage determinant de voilures
EP97917554A Revoked EP0888201B1 (fr) 1996-03-22 1997-03-21 Assemblage determinant d'aileron

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP97917567A Expired - Lifetime EP0888202B1 (fr) 1996-03-22 1997-03-21 Montage determinant de voilures

Country Status (8)

Country Link
US (2) US6314630B1 (fr)
EP (2) EP0888202B1 (fr)
JP (4) JP4234792B2 (fr)
CN (2) CN1092555C (fr)
AU (2) AU2584497A (fr)
CA (1) CA2244747C (fr)
DE (2) DE69735994T2 (fr)
WO (2) WO1997034734A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8567066B2 (en) 2010-09-28 2013-10-29 Airbus Operations Limited Aircraft rib-spar joint
CN111086225A (zh) * 2019-12-13 2020-05-01 西安飞机工业（集团）有限责任公司 一种飞机机身筒段复材壁板环向t型长桁的定位方法
IT202000018625A1 (it) * 2020-07-30 2022-01-30 Leonardo Spa Dispositivo ausiliario per la guida di un trapano e per l'aspirazione di polvere e sfridi

Families Citing this family (199)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH0591431U (ja) * 1992-04-30 1993-12-14 豊 小室 柄の一端をリングにした歯ブラシ
US7509740B2 (en) * 2001-11-13 2009-03-31 The Boeing Company Method of manufacturing a wing
US6625866B2 (en) * 1996-03-22 2003-09-30 The Boeing Company Determinant passively-located pogo machine
EP1005052B1 (fr) * 1998-06-10 2012-11-28 The Furukawa Electric Co., Ltd. Procede d'assemblage d'un transformateur d'isolation
BE1012781A3 (fr) 1999-07-09 2001-03-06 Sonaca Sa Procede d'assemblage d'un panneau souple sur une structure ouverte et installation pour la mise en oeuvre de ce procede.
GB0008302D0 (en) * 2000-04-06 2000-05-24 British Aerospace Assembly method
US6430796B1 (en) * 2000-05-03 2002-08-13 The Boeing Company Apparatus for performing automated manufacturing operations on panel-shaped workpieces
US6496745B1 (en) 2000-05-17 2002-12-17 Lockheed Martin Corporation Integration of self-locating feature into detail parts
GB0112559D0 (en) 2000-09-14 2001-07-11 Bae Systems Plc A method and control system for generating machine tool control data
US6386481B1 (en) * 2001-01-08 2002-05-14 Patria Finavicomp Oy Arrangement for fastening stringers to aircraft wing ribs
US6855099B2 (en) * 2001-10-31 2005-02-15 The Boeing Company Manufacturing system for aircraft structures and other large structures
US6661955B1 (en) 2002-02-04 2003-12-09 Siwave, Inc. Kinematic and non-kinematic passive alignment assemblies and methods of making the same
US6850675B1 (en) 2002-02-04 2005-02-01 Siwave, Inc. Base, payload and connecting structure and methods of making the same
US6674585B1 (en) 2002-02-04 2004-01-06 Siwave, Inc. Flexure assemblies and methods of making the same
US7813634B2 (en) 2005-02-28 2010-10-12 Tessera MEMS Technologies, Inc. Autofocus camera
US6779272B2 (en) 2002-08-30 2004-08-24 The Boeing Company Single piece flow based wing assembly system
US6765436B1 (en) 2002-09-04 2004-07-20 Cirrus Logic, Inc. Power supply based audio compression for digital audio amplifier
US6811120B1 (en) * 2003-04-15 2004-11-02 Adam Aircraft Industries, Inc. Modular spar tunnel
US7141191B2 (en) * 2003-05-02 2006-11-28 The Boeing Company Triple purpose lay-up tool
DE10319926B4 (de) * 2003-05-02 2006-09-28 Airbus Deutschland Gmbh Verfahren zum Ausgleichen eines Fügespaltes
DE10361391A1 (de) * 2003-12-29 2005-08-04 Airbus Deutschland Gmbh Seitenleitwerksanschluss
EP1701882B1 (fr) * 2004-01-05 2008-03-05 Airbus Deutschland GmbH Dispositif d'isolation pour l'isolation interne d'un vehicule
RU2373109C2 (ru) * 2004-01-05 2009-11-20 Эйрбас Дойчланд Гмбх Конструкция изоляционного комплекта для изоляции внутренней стороны фюзеляжа летательного аппарата
US7194326B2 (en) † 2004-02-06 2007-03-20 The Boeing Company Methods and systems for large-scale airframe assembly
FR2865954B1 (fr) * 2004-02-10 2006-06-23 Airbus France Procede et dispositif d'usinage par fenetrage de panneaux minces non-developpables
CA2532042C (fr) * 2004-02-20 2009-10-20 Bell Helicopter Textron Inc. Procede permettant de fabriquer des parties interchangeables et remplacables
DE102004018579A1 (de) * 2004-04-16 2005-11-03 Airbus Deutschland Gmbh Verkleidung für eine Struktur eines Flugzeugs
US8276847B2 (en) * 2004-04-16 2012-10-02 Airbus Operations Gmbh Cover for an aircraft structure
US7188506B2 (en) * 2004-04-21 2007-03-13 Northrop Grumman Corporation Apparatus and method utilizing an automated machine tool system and mandrel for cold working of holes in metal components
FR2870821B1 (fr) * 2004-05-25 2007-08-17 Airbus France Sas Aeronef comprenant un dispositif de detection et/ou de mesure de perturbations atmospheriques
US20060010689A1 (en) * 2004-07-14 2006-01-19 Ali Salour Automated drill process for two-diameter holes in multi-layer variable thickness composite materials
FR2873347B1 (fr) * 2004-07-22 2006-11-17 Airbus France Sas Dispositif d'eclissage d'elements de structure composite avec des elements de structure metallique
FI118122B (fi) * 2004-10-08 2007-07-13 Patria Aerostructures Oy Ilma-aluksen kääntyvä paneeli ja komposiittirakenteinen tukikappale
DE102004051915B4 (de) * 2004-10-26 2012-11-22 Airbus Operations Gmbh Vorrichtung zur Bearbeitung von Bauteilen für Verkehrsmittel
US7494318B2 (en) * 2005-02-11 2009-02-24 General Electric Company Methods and apparatus useful for servicing engines
FR2883548B1 (fr) * 2005-03-23 2007-06-15 Airbus France Sas Dispositif et procede d'eclissage mixte carbone-metal dissymetrique
DE102005038857B4 (de) * 2005-08-17 2010-03-18 Airbus Deutschland Gmbh Doppelschalig aufgebauter Mittelkasten
US20070051851A1 (en) * 2005-09-02 2007-03-08 The Boeing Company Multi-piece fastener for limited clearance applications
US8142126B2 (en) * 2005-09-02 2012-03-27 The Boeing Company Multi-piece fastener with self-indexing nut
GB0525691D0 (en) * 2005-12-16 2006-01-25 Airbus Uk Ltd A fastener assembly
ATE488429T1 (de) † 2006-01-11 2010-12-15 Boeing Co Aus verbundplatten und metallplatten zusammengesetzte flugzeugtragfläche
GB0614837D0 (en) * 2006-07-26 2006-09-06 Airbus Uk Ltd A stringer for an aircraft wing and a method of forming thereof
JP4657189B2 (ja) 2006-11-02 2011-03-23 本田技研工業株式会社 飛行機の翼構造
GB0624208D0 (en) * 2006-12-04 2007-01-10 Airbus Uk Ltd Composite structure
US7849729B2 (en) * 2006-12-22 2010-12-14 The Boeing Company Leak detection in vacuum bags
CN100491202C (zh) * 2007-04-12 2009-05-27 沈阳飞机工业（集团）有限公司 数字化装配有空间复合角度定位器工装的方法
US8568551B2 (en) 2007-05-22 2013-10-29 The Boeing Company Pre-patterned layup kit and method of manufacture
US9770871B2 (en) 2007-05-22 2017-09-26 The Boeing Company Method and apparatus for layup placement
FR2916417B1 (fr) * 2007-05-23 2009-07-24 Airbus France Sas Element structural d'aeronef situe a l'interface entre une aile et le fuselage
DE102007029500B4 (de) * 2007-06-25 2013-02-14 Airbus Operations Gmbh Verfahren zum Koppeln von Versteifungsprofilelementen sowie Strukturbauteil
US8936695B2 (en) 2007-07-28 2015-01-20 The Boeing Company Method for forming and applying composite layups having complex geometries
US8707766B2 (en) 2010-04-21 2014-04-29 The Boeing Company Leak detection in vacuum bags
US8333864B2 (en) * 2008-09-30 2012-12-18 The Boeing Company Compaction of prepreg plies on composite laminate structures
GB0720704D0 (en) * 2007-10-23 2007-12-05 Airbus Uk Ltd An aerofoil structure and a method of making a rib for an aerofoil structure
DE102007055233A1 (de) * 2007-11-20 2009-05-28 Airbus Deutschland Gmbh Kupplungsvorrichtung zum Zusammenfügen von Rumpfsektionen, Kombination aus einer Kupplungsvorrichtung und zumindest einer Rumpfsektion sowie Verfahren zur Herstellung der Kupplungsvorrichtung
US8916010B2 (en) * 2007-12-07 2014-12-23 The Boeing Company Composite manufacturing method
US8752293B2 (en) 2007-12-07 2014-06-17 The Boeing Company Method of fabricating structures using composite modules and structures made thereby
US7977583B2 (en) * 2007-12-13 2011-07-12 Teradyne, Inc. Shielded cable interface module and method of fabrication
JP4990177B2 (ja) * 2008-02-14 2012-08-01 本田技研工業株式会社 飛行機の翼構造
US8301302B2 (en) * 2008-05-08 2012-10-30 The Boeing Company Synchronous robotic operation on a structure having a confined space
ES2357489B1 (es) * 2008-05-19 2012-03-05 Airbus Operations, S.L. Procedimiento y útil de montaje de cajones de torsión para uso aeron�?utico.
GB0813584D0 (en) 2008-07-25 2008-09-03 Airbus Uk Ltd Method of stiffening a rib
JP5112361B2 (ja) * 2009-02-27 2013-01-09 三菱重工業株式会社 航空機構造体製造装置
US8539658B2 (en) * 2009-08-31 2013-09-24 The Boeing Company Autonomous carrier for continuously moving wing assembly line
CN101695814B (zh) * 2009-10-15 2011-01-19 浙江大学 一种飞机大部件精确入位的方法及其装置
US20110119919A1 (en) * 2009-11-23 2011-05-26 The Boeing Company Determinant Assembly System for Manufacturing Objects
US8661684B1 (en) 2010-01-21 2014-03-04 The Boeing Company High rate pulsing wing assembly line
CN101804565B (zh) * 2010-02-10 2011-12-14 中捷机床有限公司 用于飞机整机精加工及装配的生产线
GB201008186D0 (en) * 2010-05-17 2010-06-30 Airbus Operations Ltd A structural assembly for an aircraft
DE102010022582A1 (de) * 2010-06-03 2011-12-08 Brötje-Automation GmbH Verfahren zur Steuerung einer getakteten Fertigungsstraße
GB201009922D0 (en) * 2010-06-14 2010-07-21 Airbus Uk Ltd Aircraft wing box joint
CN102059549B (zh) * 2010-11-12 2012-11-21 浙江大学 基于四个数控定位器的飞机发动机调姿安装系统及使用方法
ES2402463B1 (es) * 2010-11-30 2014-03-13 Airbus Operations, S.L. Un revestimiento de una superficie sustentadora de una aeronave.
CN102060100B (zh) * 2010-12-14 2013-03-27 钱智声 飞机机身-机翼连接机构
JP5769412B2 (ja) 2010-12-17 2015-08-26 三菱重工業株式会社 構造物製造方法
JP5851699B2 (ja) 2011-02-10 2016-02-03 三菱重工業株式会社 大型構造物の組み立てに用いる組立治具
JP5535957B2 (ja) * 2011-02-21 2014-07-02 三菱航空機株式会社 翼パネルの形成方法
JP5848012B2 (ja) 2011-03-03 2016-01-27 三菱重工業株式会社 工作機械
CN102179782B (zh) * 2011-04-07 2012-09-05 中国航空工业集团公司北京航空制造工程研究所 一种复合材料翼面整体构件骨架或加筋的定位工装及其使用方法
US9032602B2 (en) 2011-07-15 2015-05-19 The Boeing Company Methods and systems for in-process quality control during drill-fill assembly
KR101362213B1 (ko) 2011-11-18 2014-02-17 김성남 비행기 날개 프로파일 몰드 및 그 제조공법
GB201120707D0 (en) 2011-12-01 2012-01-11 Airbus Operations Ltd Leading edge structure
US9014836B2 (en) 2011-12-15 2015-04-21 The Boeing Company Autonomous carrier system for moving aircraft structures
US9090357B2 (en) * 2011-12-15 2015-07-28 The Boeing Company Method of assembling panelized aircraft fuselages
CN102513941A (zh) * 2011-12-16 2012-06-27 陕西飞机工业（集团）有限公司 一种可调式机翼整体壁板喷丸强化模拟试验工装
JP5928941B2 (ja) * 2012-02-24 2016-06-01 エアバス オペレーションズ リミテッドＡｉｒｂｕｓ Ｏｐｅｒａｔｉｏｎｓ Ｌｉｍｉｔｅｄ 航空機のリブ−桁接合部
US9180956B1 (en) * 2012-04-11 2015-11-10 The Boeing Company Methods and apparatus for attaching an aircraft wing assembly to an aircraft body
CN102680262B (zh) * 2012-05-15 2014-11-19 上海交通大学 飞机机翼缘条装配模拟实验台
DE102012209320A1 (de) * 2012-06-01 2013-12-05 Airbus Operations Gmbh Verfahren und Lagervorrichtung zum Lagern und Ausrichten eines Bauteils
CN102700726B (zh) * 2012-06-15 2014-10-15 西北工业大学 一种三坐标的双支臂定位器
CN102721563B (zh) * 2012-06-28 2014-10-15 上海交通大学 飞机机翼长桁装配模拟实验装置
EP2700574B1 (fr) * 2012-08-22 2016-08-17 Airbus Operations GmbH Réduction de charge passive pour caisson central à fibres renforcées d'un avion ayant une structure de coque rigide
US20140060197A1 (en) * 2012-08-31 2014-03-06 The Boeing Company Ultrasonic array transducer holder and guide for flanges having cutouts and asymmetric geometry
US9943937B2 (en) 2012-09-28 2018-04-17 The Boeing Company System and method for manufacturing a wing panel
KR101416830B1 (ko) 2012-10-15 2014-07-08 한국항공우주산업 주식회사 항공기의 주구조물 고정용 치구
US8857765B2 (en) * 2012-10-16 2014-10-14 The Boeing Company Method and apparatus for attaching an aircraft fuselage frame to a wing box
RU2509038C1 (ru) * 2012-11-01 2014-03-10 Открытое акционерное общество "Национальный институт авиационных технологий" (ОАО НИАТ) Стапель для сборки аэродинамического органа управления летательного аппарата
CN103063333B (zh) * 2012-12-19 2014-11-05 北京航空航天大学 一种飞机框类零件装配应力检测与控制方法
US20140272312A1 (en) * 2013-03-13 2014-09-18 Gulfstream Aerospace Corporation Aircraft component and method of making an aircraft component
CN103204236B (zh) * 2013-04-24 2015-07-01 哈尔滨飞机工业集团有限责任公司 一种用于直升机的多用途外挂装置
FR3005121B1 (fr) * 2013-04-30 2015-05-22 Airbus Operations Sas Dispositif de guidage destine a etre interpose entre un dispositif de fixation de pieces d'un assemblage, et un dispositif de protection du dispositif de fixation
US9573198B1 (en) 2013-06-06 2017-02-21 The Boeing Company Double eccentric positioning apparatus
US9068809B1 (en) 2013-06-06 2015-06-30 The Boeing Company Quasi-virtual locate/drill/shim process
US9227718B2 (en) * 2013-06-07 2016-01-05 The Boeing Company Lower joints between outboard wing boxes and center wing sections of aircraft wing assemblies
US9266623B2 (en) 2013-06-25 2016-02-23 The Boeing Company Modular stanchion system
US9272793B2 (en) 2013-06-25 2016-03-01 The Boeing Company Modular stanchion system
US9580164B2 (en) * 2013-07-10 2017-02-28 The Boeing Company Apparatus and methods for joining aircraft composite structures
CN103433717B (zh) * 2013-08-15 2015-06-03 中国航空工业集团公司北京航空制造工程研究所 用于机翼壁板自动上下架的装置
WO2015038041A1 (fr) 2013-09-11 2015-03-19 Saab Ab Dispositif de fixation pour la fabrication de structures aéronautiques et procédé pour la mise en œuvre dudit dispositif
ES2674659T3 (es) * 2013-09-23 2018-07-03 Airbus Operations S.L. Método para fabricar una caja de torsión aeronáutica, caja de torsión y herramienta para fabricar una caja de torsión aeronáutica
EP2853963A1 (fr) * 2013-09-30 2015-04-01 BAE Systems PLC Production d'objet
EP2889214B1 (fr) * 2013-12-31 2020-02-05 Airbus Operations, S.L. Boîte infusée hautement intégrée constituée d'un matériau composite et procédé de fabrication
US9579875B2 (en) * 2014-02-04 2017-02-28 The Boeing Company Bonded tab and tooling device
US10343193B2 (en) 2014-02-24 2019-07-09 The Boeing Company System and method for surface cleaning
CN103934682B (zh) * 2014-04-14 2016-04-13 上海交通大学 飞机机翼楔形翼梁装配模拟实验台
EP2937754A1 (fr) * 2014-04-24 2015-10-28 BAE Systems PLC Ensemble de cellules d'aéronef
US10691097B2 (en) 2014-05-09 2020-06-23 The Boeing Company Path repeatable machining for full sized determinant assembly
DE102014017596A1 (de) * 2014-05-16 2015-11-19 Liebherr-Aerospace Lindenberg Gmbh Flash FAL Track II
DE102014111747B4 (de) 2014-08-18 2021-11-04 Airbus Operations Gmbh Bearbeitungsvorrichtung zur Montage von Luftfahrzeugen
WO2016053259A1 (fr) 2014-09-29 2016-04-07 The Boeing Company Longerons infléchis pour applications de gouvernail et de gouverne de profondeur
KR101687562B1 (ko) * 2014-12-31 2016-12-19 한국항공우주산업 주식회사 회전익 항공기의 동체 자동 장착 및 탈착 장치
CN104554704B (zh) * 2015-01-27 2016-09-28 新誉集团有限公司 可横向组装的大展弦比机翼结构及其组装方法
JP6523693B2 (ja) * 2015-01-28 2019-06-05 三菱重工業株式会社 航空機部品位置決め装置、航空機組立システム及び航空機組立方法
US10144530B1 (en) 2015-05-04 2018-12-04 The Boeing Company Model-based definition for machining aircraft parts
US9925625B2 (en) * 2015-05-04 2018-03-27 The Boeing Company Assembly of an aircraft structure assembly without shimming, locating fixtures or final-hole-size drill jigs
US9857789B2 (en) 2015-05-04 2018-01-02 The Boeing Company Model-based definition for machining aircraft parts
KR101701745B1 (ko) * 2015-06-01 2017-02-06 한국항공우주산업 주식회사 항공기 날개 제조용 물류장치
KR101698351B1 (ko) * 2015-06-03 2017-01-23 한국항공우주산업 주식회사 항공기 날개 부품 결합을 위한 자동화 장비
CN106275494A (zh) * 2015-06-05 2017-01-04 陕西飞机工业（集团）有限公司 飞机装配工装用整体底座式标准工艺装备
US9962834B2 (en) 2015-06-17 2018-05-08 The Boeing Company Compliant end effectors, robots that include compliant end effectors, and methods of utilizing the same
US9725184B2 (en) * 2015-06-18 2017-08-08 The Boeing Company Methods for sealing an internal composite vent stringer
WO2017021722A1 (fr) * 2015-08-05 2017-02-09 Bae Systems Plc Assemblage de pièces d'aéronefs
CN105035356A (zh) * 2015-08-18 2015-11-11 江西洪都航空工业集团有限责任公司 一种多点共面高精度孔轴配合飞机部件对接协调方法
JP6498568B2 (ja) * 2015-08-27 2019-04-10 三菱重工業株式会社 組立体製造装置及び組立体製造方法
CN105253291A (zh) * 2015-10-14 2016-01-20 哈尔滨飞机工业集团有限责任公司 一种带梳状接头的机翼整体机加壁板及应用
US10275565B2 (en) 2015-11-06 2019-04-30 The Boeing Company Advanced automated process for the wing-to-body join of an aircraft with predictive surface scanning
US10521551B2 (en) 2015-11-16 2019-12-31 The Boeing Company Methods for shimming flexible bodies
US9849966B2 (en) 2015-12-18 2017-12-26 The Boeing Company Fuselage structure for accommodating tails and canards of different sizes and shapes
US20170210489A1 (en) * 2016-01-22 2017-07-27 The Boeing Company Methods and systems for wing-to-body joining
JP6513585B2 (ja) 2016-02-02 2019-05-15 三菱重工業株式会社 形状保持治具及び航空機パネル製造方法
JP6513584B2 (ja) 2016-02-02 2019-05-15 三菱重工業株式会社 保持治具固定装置
JP6650147B2 (ja) 2016-02-02 2020-02-19 三菱重工業株式会社 航空機パネル製造方法及び航空機パネル製造システム
US10513325B2 (en) 2016-02-08 2019-12-24 Bell Helicopter Textron Inc. Joint member for a composite wing structure
US10639854B2 (en) 2016-02-08 2020-05-05 Bell Helicopter Textron Inc. Composite wing structure and methods of manufacture
US11142297B2 (en) 2016-02-08 2021-10-12 Bell Helicopter Textron Inc. Heating tool
KR101745936B1 (ko) 2016-06-16 2017-06-12 주식회사 신라금속 프로펠러 가공용 지그세트
CN106239034A (zh) * 2016-08-19 2016-12-21 成都飞机工业（集团）有限责任公司 一种在曲面上准确按法矢方向手工制孔的方法
US10179640B2 (en) * 2016-08-24 2019-01-15 The Boeing Company Wing and method of manufacturing
US10324426B2 (en) * 2016-10-26 2019-06-18 Embraer S.A. Automated system and method to manufacture aeronautic junction parts
US10766594B2 (en) * 2016-11-03 2020-09-08 Continuous Composites Inc. Composite vehicle body
EP3539716A4 (fr) 2016-11-11 2020-07-01 Mitsubishi Heavy Industries, Ltd. Procédé de production d'élément et système de production d'élément
CN106736508A (zh) * 2016-11-29 2017-05-31 湖北三江航天红阳机电有限公司 一种折叠尾翼的铆接装配装置及方法
KR101864051B1 (ko) * 2016-12-23 2018-06-01 양용만 복합재를 이용한 경량 날개 및 블레이드 제조방법
CN107044825A (zh) * 2017-03-16 2017-08-15 亿信标准认证集团有限公司 一种关于零件加工尺寸标准认证的检测方法及检测系统
US10814480B2 (en) * 2017-06-14 2020-10-27 The Boeing Company Stabilization of tool-carrying end of extended-reach arm of automated apparatus
WO2018229969A1 (fr) 2017-06-16 2018-12-20 三菱重工業株式会社 Dispositif de fabrication de structure d'aéronef
US11181882B2 (en) * 2017-06-19 2021-11-23 The Boeing Company Dynamic modification of production plans responsive to manufacturing deviations
CN107350785B (zh) * 2017-08-14 2019-09-17 上海卫星装备研究所 一种高精度多维度联动结构装配装置及装配方法
US10654208B2 (en) 2017-09-20 2020-05-19 Bell Helicopter Textron Inc. Assembly fixture with anisotropic thermal properties
CN107538195A (zh) * 2017-09-26 2018-01-05 陕西飞机工业（集团）有限公司 一种超长机翼装配协调展长方法
CN109204873B (zh) * 2017-10-30 2020-09-08 中国航空制造技术研究院 一种飞机中央翼盒数字化装配定位系统及定位方法
CN108326590A (zh) * 2018-04-02 2018-07-27 南京合信自动化有限公司 一种快速定位夹具和定位系统
RU2704679C2 (ru) * 2018-04-16 2019-10-30 федеральное государственное бюджетное образовательное учреждение высшего образования "Тольяттинский государственный университет" Сборочный стапель
JP7118745B2 (ja) * 2018-05-30 2022-08-16 三菱重工業株式会社 加工装置及び加工方法
CN108917677B (zh) * 2018-07-19 2020-03-17 福建天晴数码有限公司 立方体房间内部尺寸测量方法、存储介质
US10712730B2 (en) 2018-10-04 2020-07-14 The Boeing Company Methods of synchronizing manufacturing of a shimless assembly
US11136107B2 (en) 2018-10-05 2021-10-05 The Boeing Company Method and apparatus for attaching a fuselage frame to a wing box
CN109263860B (zh) * 2018-11-19 2024-07-23 中国商用飞机有限责任公司北京民用飞机技术研究中心 一种机翼翼梁及机翼
EP3708483B1 (fr) * 2019-03-14 2021-09-15 SFS Intec Holding AG Dispositif de maintien pour modules muraux
SG11202111294QA (en) * 2019-04-25 2021-11-29 Aerovironment Inc Ground support equipment for a high altitude long endurance aircraft
JP7472169B2 (ja) 2019-04-25 2024-04-22 エアロバイロメント，インコーポレイテッド 高高度長航続時間航空機の上昇及び滑空動作の方法
US11518514B2 (en) 2019-04-25 2022-12-06 Aerovironment, Inc Off-center parachute flight termination system including latch mechanism disconnectable by burn wire
US11162425B2 (en) 2019-06-11 2021-11-02 Rolls-Royce Corporation Assembly fixture
CN110293365B (zh) * 2019-07-19 2024-05-31 中国重型机械研究院股份公司 一种扇形段抽出导轨安装定位方法以及瞄准筒
CN110625381B (zh) * 2019-08-26 2024-05-24 格力电器（石家庄）有限公司 一种接线支架组件预装用自动化装置及其使用方法
JP7324109B2 (ja) * 2019-09-30 2023-08-09 株式会社Subaru 組立装置
US11305862B2 (en) * 2019-12-20 2022-04-19 The Boeing Company Joint joining an aircraft wing to an aircraft body
CN110979725B (zh) * 2020-01-02 2023-04-14 上海蓝享机械制造有限公司 一种飞机翼肋及其生产工艺
CN111186593B (zh) * 2020-01-15 2022-11-29 通航国际（西安）飞机技术有限公司 一种飞机机翼的安装方法
CN111515723B (zh) * 2020-05-12 2021-08-03 上海振华港机重工有限公司 一种用于连接支座机械加工的夹具
CN111633413B (zh) * 2020-06-09 2022-03-08 中国科学院空天信息创新研究院 用于波导法兰连接错位时的校正工具及校正方法
CN112340055B (zh) * 2020-09-30 2022-05-10 成都飞机工业（集团）有限责任公司 一种立柱式卡板定位装配型架
CN112373715A (zh) * 2020-10-14 2021-02-19 浙江大学 一种用于大型飞机机翼前缘组件上架的装置
CN112249300B (zh) * 2020-10-22 2022-02-15 航天特种材料及工艺技术研究所 一种碳纤维复合材料翼面前缘结构
US11753184B2 (en) * 2020-11-18 2023-09-12 The Boeing Company Assembly line fabrication and assembly of aircraft wings
CN112373674B (zh) * 2020-11-19 2022-08-09 航天彩虹无人机股份有限公司 传感器无人机的机翼连接结构、机翼及无人机
RU2747889C1 (ru) * 2020-11-23 2021-05-17 Закрытое акционерное общество «Авиа-Тверь-Сервис» (ЗАО «Авиа-Тверь-Сервис») Способ ремонта агрегата сотовой конструкции воздушного судна и стапель для осуществления способа
CN113044204A (zh) * 2021-04-29 2021-06-29 吉林大学 一种碳纤维机翼骨架结构
CN113277115B (zh) * 2021-07-02 2022-05-06 航天特种材料及工艺技术研究所 一种无人机机翼装配方法
CN113714757B (zh) * 2021-08-20 2023-06-23 西安飞机工业（集团）有限责任公司 一种翼肋与梁结构装配的定位靠尺及定位方法
CN113664530B (zh) * 2021-09-06 2022-09-13 上海航天精密机械研究所 一种助推尾段型架尾翼对接接头的定位装置及装配方法
CN114013680B (zh) * 2021-11-19 2023-04-18 航天特种材料及工艺技术研究所 一种机翼端肋的装配型架及机翼对接安装座的装配方法
EP4215444A1 (fr) * 2022-01-20 2023-07-26 Airbus Operations GmbH Procédé d'assemblage d'une structure dans la fabrication d'un aéronef ou d'un engin spatial
CN114476015B (zh) * 2022-03-28 2022-08-16 沃飞长空科技(成都)有限公司 无人机部件快拆机构及无人机
CN115070451B (zh) * 2022-07-22 2023-06-13 大连理工大学 一种壁板整体形变可控的移动式柔性夹具及操控方法
CN115057000B (zh) * 2022-08-16 2022-11-01 中国空气动力研究与发展中心空天技术研究所 高超声速飞行器空气舵系统零位校准装置及校准方法
PL443186A1 (pl) * 2022-12-19 2024-06-24 Wytwórnia Zespołów Kooperacyjnych Spółka Z Ograniczoną Odpowiedzialnością Sposób wykonania elementu mechanizacji skrzydła samolotu, zwłaszcza klapy przedniej
CN116921738B (zh) * 2023-09-19 2023-12-12 辽宁华天航空科技股份有限公司 一种用于飞机大夹层盲孔结构反孔的加工设备及工艺
CN118342246B (zh) * 2024-06-18 2024-09-24 广联航空(自贡)有限公司 一种机翼组装装置

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4310964A (en) * 1979-01-02 1982-01-19 The Boeing Company Method and apparatus for the automated assembly of major subassemblies
US4995146A (en) * 1988-10-26 1991-02-26 The Boeing Company Assembly jig and method for making wing spars
EP0593127A1 (fr) * 1992-10-13 1994-04-20 The Boeing Company Assemblage de panneau et de fuselage

Family Cites Families (42)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US514276A (en) * 1894-02-06 Pierre de p
US1352647A (en) * 1920-05-21 1920-09-14 Ottis A Mcdill Double clamp
US1989141A (en) * 1931-02-05 1935-01-29 George Ramsey Shingle guide
US2242147A (en) * 1938-12-30 1941-05-13 Bell Aircraft Corp Hinge fitting
US2330185A (en) * 1940-12-05 1943-09-21 Vultee Aircraft Inc Airplane wing construction
US2324435A (en) * 1941-09-15 1943-07-13 Cons Aircraft Corp Method of making flanged elements
US2378043A (en) * 1942-10-24 1945-06-12 Ford Motor Co Method of airframe assembly
US2483134A (en) * 1945-05-01 1949-09-27 Republic Aviat Corp Airfoil
US2567124A (en) * 1946-05-10 1951-09-04 Curtiss Wright Corp Airfoil construction
US2881994A (en) * 1953-11-09 1959-04-14 Northrop Aircraft Inc Convex panel wing construction
US2865585A (en) * 1954-03-15 1958-12-23 Thomas W Beyer Universal jacking support for engines and transmissions
US2896893A (en) * 1956-04-16 1959-07-28 Oliver Mariano Accessory for venetian blinds
US3002717A (en) * 1960-01-12 1961-10-03 Pavlecka John Airfoil structure
US3301513A (en) * 1965-05-28 1967-01-31 Sugaya Masao Beam clamp and clip assemblies
US3643900A (en) * 1970-03-02 1972-02-22 John P Maloney Jig panel for airfoil
US3703762A (en) * 1971-04-12 1972-11-28 Fmc Corp Method of aligning forms
US4213587A (en) * 1978-12-04 1980-07-22 The Boeing Company Hinge arrangement for control surfaces
US4203204A (en) * 1979-01-02 1980-05-20 The Boeing Company Apparatus for the automated assembly of major subassemblies
DE2948690C2 (de) * 1979-12-04 1983-06-30 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Formschale, insbesondere Laminierformschale
US4498647A (en) * 1982-03-15 1985-02-12 Mcdonnel Douglas Corporation Surface hold-down mechanism
US4717097A (en) * 1986-03-03 1988-01-05 The Boeing Company Aircraft wings with aileron-supported ground speed spoilers and trailing edge flaps
US4887341A (en) * 1986-09-01 1989-12-19 Mazda Motor Corporation Method and apparatus for fitting component sections
US5248074A (en) * 1987-12-02 1993-09-28 Gemcor Engineering Corp. Five axis riveter and system
US4885836A (en) * 1988-04-19 1989-12-12 Imta Riveting process and apparatus
US4894903A (en) * 1988-07-06 1990-01-23 The Boeing Company Assembly jig and method for making wing panels
JPH02284885A (ja) * 1989-04-27 1990-11-22 Nissan Motor Co Ltd ワーク位置決め装置の位置教示方法
US5050288A (en) * 1989-12-15 1991-09-24 The Boeing Company Dynamic dimensional control matrix system
US5033695A (en) * 1990-01-23 1991-07-23 Foshee Paul L Aileron counterbalance mount bracket
US5142764A (en) * 1990-11-28 1992-09-01 The United States Of America As Represented By The Secretary Of The Air Force Method for tack-free positioning of aircraft components for subsequent fastening
US5135206A (en) * 1991-05-13 1992-08-04 Martinez Ramiro H Routable stock clamping device
US5341556A (en) * 1991-06-28 1994-08-30 The United States Of America As Represented By The Secretary Of The Air Force Method and apparatus for manufacture of reinforced panels
US5265317A (en) * 1991-12-19 1993-11-30 Progressive Tool & Industries Co. Geometry station
US5288209A (en) * 1991-12-19 1994-02-22 General Electric Company Automatic adaptive sculptured machining
US5246316A (en) * 1992-03-06 1993-09-21 Excellon Automation Work table orientation apparatus and method
US5283943A (en) * 1992-08-31 1994-02-08 Kermit Aguayo Automated assembly apparatus
US5477596A (en) * 1992-12-23 1995-12-26 The Boeing Company Stringer/clip placement and drilling
US5299894A (en) * 1992-12-23 1994-04-05 The Boeing Company Workpiece positioning and drilling end effector
GB2276600B (en) * 1993-04-01 1996-07-31 British Aerospace Manufacture of aircraft wings
US5615474A (en) * 1994-09-09 1997-04-01 Gemcor Engineering Corp. Automatic fastening machine with statistical process control
US6029352A (en) * 1997-09-25 2000-02-29 The Boeing Company Wing panel assembly
ES2156660B1 (es) * 1998-01-14 2002-02-16 Saiz Manuel Munoz Mandos de vuelo con compensacion automatica.
US6122819A (en) * 1999-03-29 2000-09-26 Daimlerchrysler Corporation Mechanism for positioning a pair of hinges on an automobile body

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4310964A (en) * 1979-01-02 1982-01-19 The Boeing Company Method and apparatus for the automated assembly of major subassemblies
US4995146A (en) * 1988-10-26 1991-02-26 The Boeing Company Assembly jig and method for making wing spars
EP0593127A1 (fr) * 1992-10-13 1994-04-20 The Boeing Company Assemblage de panneau et de fuselage

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of WO9734733A1 *

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8567066B2 (en) 2010-09-28 2013-10-29 Airbus Operations Limited Aircraft rib-spar joint
EP2433860A3 (fr) * 2010-09-28 2016-03-16 Airbus Operations Limited Joint nervure-longeron d'aéronef
CN111086225A (zh) * 2019-12-13 2020-05-01 西安飞机工业（集团）有限责任公司 一种飞机机身筒段复材壁板环向t型长桁的定位方法
IT202000018625A1 (it) * 2020-07-30 2022-01-30 Leonardo Spa Dispositivo ausiliario per la guida di un trapano e per l'aspirazione di polvere e sfridi
WO2022024063A1 (fr) * 2020-07-30 2022-02-03 Leonardo S.P.A. Dispositif auxiliaire pour guider un foret et pour aspirer des poussières et des déchets

Also Published As

Publication number Publication date
CN1089049C (zh) 2002-08-14
EP0888201B1 (fr) 2006-05-31
JP2000506816A (ja) 2000-06-06
US6808143B2 (en) 2004-10-26
DE69735994D1 (de) 2006-07-06
JP2008037423A (ja) 2008-02-21
DE69735994T2 (de) 2007-01-11
JP4234792B2 (ja) 2009-03-04
JP2000506815A (ja) 2000-06-06
AU2584497A (en) 1997-10-10
WO1997034733A1 (fr) 1997-09-25
CN1092555C (zh) 2002-10-16
EP0888202A4 (fr) 2002-05-15
JP4128626B2 (ja) 2008-07-30
AU2585397A (en) 1997-10-10
CN1213999A (zh) 1999-04-14
CA2244747A1 (fr) 1997-09-25
WO1997034734A1 (fr) 1997-09-25
DE69733941D1 (de) 2005-09-15
US20020078545A1 (en) 2002-06-27
CA2244747C (fr) 2006-01-17
US6314630B1 (en) 2001-11-13
JP4627542B2 (ja) 2011-02-09
EP0888201A4 (fr) 2002-05-15
JP4351716B2 (ja) 2009-10-28
DE69733941T2 (de) 2006-06-14
EP0888202A1 (fr) 1999-01-07
JP2008007114A (ja) 2008-01-17
CN1213998A (zh) 1999-04-14
EP0888202B1 (fr) 2005-08-10

Similar Documents

Publication Publication Date Title
EP0888201B1 (fr) Assemblage determinant d'aileron
US6170157B1 (en) Determinant spar assembly
US8695219B2 (en) Determinant wing assembly
US5615483A (en) Method of assembling parts on an aircraft skin to form a panel
US6779272B2 (en) Single piece flow based wing assembly system
EP1221353B1 (fr) Machine déterminante avec ajustement passif des dispositifs de positionnement "Pogo"
CA2554189C (fr) Ensemble de fabrication d'ailes determinant
CA2583586C (fr) Assemblage determinant d'aileron
CA2522914C (fr) Assemblage determinant d'aileron
CA2242868C (fr) Montage determinant de voilures
Hartman et al. Wing manufacturing-Next generation

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 19980810

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB

A4 Supplementary search report drawn up and despatched

Effective date: 20020328

AK Designated contracting states

Kind code of ref document: A4

Designated state(s): DE FR GB

17Q First examination report despatched

Effective date: 20021127

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REF Corresponds to:

Ref document number: 69735994

Country of ref document: DE

Date of ref document: 20060706

Kind code of ref document: P

ET Fr: translation filed
PLBI Opposition filed

Free format text: ORIGINAL CODE: 0009260

PLAX Notice of opposition and request to file observation + time limit sent

Free format text: ORIGINAL CODE: EPIDOSNOBS2

26 Opposition filed

Opponent name: AIRBUS DEUTSCHLAND GMBH/AIRBUS FRANCE SAS/AIRBUS U

Effective date: 20070228

PLAF Information modified related to communication of a notice of opposition and request to file observations + time limit

Free format text: ORIGINAL CODE: EPIDOSCOBS2

PLBB Reply of patent proprietor to notice(s) of opposition received

Free format text: ORIGINAL CODE: EPIDOSNOBS3

APAH Appeal reference modified

Free format text: ORIGINAL CODE: EPIDOSCREFNO

APBM Appeal reference recorded

Free format text: ORIGINAL CODE: EPIDOSNREFNO

APBP Date of receipt of notice of appeal recorded

Free format text: ORIGINAL CODE: EPIDOSNNOA2O

APBQ Date of receipt of statement of grounds of appeal recorded

Free format text: ORIGINAL CODE: EPIDOSNNOA3O

PLAB Opposition data, opponent's data or that of the opponent's representative modified

Free format text: ORIGINAL CODE: 0009299OPPO

R26 Opposition filed (corrected)

Opponent name: AIRBUS DEUTSCHLAND GMBH/AIRBUS FRANCE SAS/AIRBUS U

Effective date: 20070228

APBU Appeal procedure closed

Free format text: ORIGINAL CODE: EPIDOSNNOA9O

REG Reference to a national code

Ref country code: DE

Ref legal event code: R103

Ref document number: 69735994

Country of ref document: DE

Ref country code: DE

Ref legal event code: R064

Ref document number: 69735994

Country of ref document: DE

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20130327

Year of fee payment: 17

Ref country code: DE

Payment date: 20130327

Year of fee payment: 17

Ref country code: FR

Payment date: 20130405

Year of fee payment: 17

RDAF Communication despatched that patent is revoked

Free format text: ORIGINAL CODE: EPIDOSNREV1

RDAG Patent revoked

Free format text: ORIGINAL CODE: 0009271

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: PATENT REVOKED

27W Patent revoked

Effective date: 20130419

GBPR Gb: patent revoked under art. 102 of the ep convention designating the uk as contracting state

Effective date: 20130419

REG Reference to a national code

Ref country code: DE

Ref legal event code: R107

Ref document number: 69735994

Country of ref document: DE

Effective date: 20140109